CN109131848B - Safe forced landing system for unmanned aerial vehicle and auxiliary device thereof - Google Patents
Safe forced landing system for unmanned aerial vehicle and auxiliary device thereof Download PDFInfo
- Publication number
- CN109131848B CN109131848B CN201811002660.8A CN201811002660A CN109131848B CN 109131848 B CN109131848 B CN 109131848B CN 201811002660 A CN201811002660 A CN 201811002660A CN 109131848 B CN109131848 B CN 109131848B
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- ball
- aerial vehicle
- protective shell
- auxiliary device
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
Abstract
The invention discloses a safe forced landing system for an unmanned aerial vehicle and an auxiliary device thereof, belonging to the field of unmanned aerial vehicle equipment, the safe forced landing system for the unmanned aerial vehicle and the auxiliary device thereof comprise an unmanned aerial vehicle body connected with a control mechanism, the control mechanism comprises a power unit, a driving unit, a control unit and a monitoring unit, the power unit, the driving unit and the monitoring unit are all connected with the control unit in a one-way manner, the power unit is connected with the driving unit in a two-way manner, the lower end of the unmanned aerial vehicle body is connected with a landing gear, the lower end of the landing gear is connected with a damping ball, a pre-embedded ball is arranged in a cavity, the safe forced landing of the unmanned aerial vehicle can be realized, when the unmanned aerial vehicle falls to the ground, the damping ball at the lower end of the landing gear is utilized to reduce the vibration, the unmanned aerial vehicle is protected, even if the damping ball cracks due to friction and collision, the damping ball can timely crack the repaired position and effectively prevent the cracked position from expanding continuously, the shock absorption effect is ensured not to be suddenly reduced to a large extent, and the protection performance is greatly improved.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicle equipment, in particular to a safe forced landing system for an unmanned aerial vehicle and an auxiliary device thereof.
Background
The four-rotor aircraft is a four-propeller aircraft with vertical take-off and landing and hovering capabilities. The device has the characteristics of easy maintenance, simple structure and high stability, and can be widely applied to the civil and military fields.
At present, the multi-rotor aircraft is driven by batteries, and the energy density of the batteries is far lower than that of fuel, so that the endurance is low, the supplementary charging is limited, and the multi-rotor aircraft is limited in practical application.
Fuel power has great advantages over battery power due to high energy density. At present, no fuel-powered multi-rotor unmanned aircraft exists in the market. Tianjin university has applied for a patent of a petrol-electric hybrid four-rotor unmanned aerial vehicle [ publication No. CN103359284A ], and the scheme has large energy loss due to two conversions from mechanical energy to electric energy and then to mechanical energy, and is insufficient in improving endurance.
In order to improve the problems, the Chinese utility model new publication No. CN204489196U discloses a fuel-powered multi-rotor unmanned aerial vehicle, which adopts a fuel engine to provide power, converts the power into electric power through a generator, drives a direct current motor to drive a rotor to rotate, and provides flight power for the unmanned aerial vehicle; when the engine is in emergency such as failure, the standby storage battery can be started to provide power, and safe forced landing is realized; simple structure, the time of endurance is prolonged greatly than the tradition through battery drive's many rotor crafts.
Unmanned aerial vehicle when falling to the ground, there will be certain vibrations, and unmanned aerial vehicle belongs to the comparatively accurate equipment of structure, and its inside part can be damaged in frequent vibrations, influences its flight performance, especially is compelled to descend under the condition in breaking down, is difficult to control, and when undercarriage contact ground, can take place the friction and collision, so add damping device on the undercarriage, but damping device in case impaired splitting open in the friction and collision, its shock attenuation effect can suddenly greatly reduced, the effect greatly reduced of protection unmanned aerial vehicle body.
Disclosure of Invention
1. Technical problem to be solved
Aiming at the problems in the prior art, the invention aims to provide a safe forced landing system for an unmanned aerial vehicle and an auxiliary device thereof, which can realize the safe forced landing of the unmanned aerial vehicle, and when the unmanned aerial vehicle falls to the ground, the vibration is reduced by using the damping ball at the lower end of the undercarriage, so that the unmanned aerial vehicle is protected, even if the damping ball cracks due to friction and collision, the repairing ball can repair the cracked part in time, effectively prevent the cracked part from being continuously expanded, ensure that the damping effect cannot be suddenly and greatly reduced, and greatly improve the protection performance.
2. Technical scheme
In order to solve the above problems, the present invention adopts the following technical solutions.
A safe forced landing system for an unmanned aerial vehicle and an auxiliary device thereof comprise an unmanned aerial vehicle body connected with a control mechanism, wherein the control mechanism comprises a power unit, a driving unit, a control unit and a monitoring unit, the power unit, the driving unit and the monitoring unit are all in one-way connection with the control unit, the power unit is in two-way connection with the driving unit, the power unit is in one-way connection with the monitoring unit, the lower end of the unmanned aerial vehicle body is connected with a landing gear, the lower end of the landing gear is connected with a damping ball, a cavity is chiseled in the landing gear, the cavity is internally provided with a pre-embedded ball, so that the safe forced landing of the unmanned aerial vehicle can be realized, when the unmanned aerial vehicle falls to the ground, the damping ball at the lower end of the landing gear is utilized to reduce the vibration, the unmanned aerial vehicle is protected, even if the damping ball cracks due to friction and collision, the remedial ball can timely crack the remedial place and effectively prevent the cracked place from continuing to expand, the shock absorption effect is ensured not to be suddenly reduced to a large extent, and the protection performance is greatly improved.
Further, the shock attenuation ball includes hollow spherical shell and shock attenuation rubber sleeve, the shock attenuation rubber sleeve wraps up in hollow spherical shell outer end, and the shock attenuation rubber sleeve splices with the undercarriage lower extreme, be connected with a plurality of connecting rods between undercarriage lower extreme and the hollow spherical shell, hollow spherical shell and shock attenuation rubber sleeve cooperate, also be favorable to alleviateing the quality of shock attenuation ball when guaranteeing the shock attenuation effect, alleviate unmanned aerial vehicle's flight burden.
Further, pre-buried ball includes first protective housing, warning ball and benefit ball, warning ball and remedy ball all fill in first protective housing inboard, first protective housing is the oxide film, and pre-buried ball can utilize its inside warning ball and the effect of remedy ball to play warning and remedy after the rubber shock-absorbing sleeve is impaired splits.
Furthermore, the distance between the connecting rods is larger than the diameter of the rescue ball and is 1.5mm-2mm, so that the rescue ball can smoothly pass through the connecting rods and enter the space between the rubber damping sleeve and the hollow spherical shell to rescue the cracked part.
Further, benefit and rescue the ball and include second protective housing and third protective housing, the second protective housing wraps up in the third protective housing outer end, the inside packing of third protective housing has the solution of remedying, and the second protective housing can make between benefit and rescue the ball to and mend and be difficult for the adhesion agglomeration between rescue the ball and the warning ball, be convenient for simultaneously mend the smooth roll-off of rescue the ball, and the third protective housing is used for protecting the solution of remedying.
Furthermore, the second protective housing is the oxide film equally, and the thickness of second protective housing is 1.2-1.5 times of first protective housing thickness, the third protective housing is 3D printing material and adopts 3D printing technique to make, mix elasticity epoxy in the remedy liquid, 3D printing material degradable also makes things convenient for the preparation of third protective housing in the environmental protection, and elasticity epoxy viscosity is high, has improved the pursuit nature of remedy liquid to the crack.
Further, the undercarriage is thermoplastic elastomer's variant material, the warning ball is hollow transparent spherical shell, warning ball inner surface scribbles fluorescent coating, and warns the ball intussuseption and fill hydrogen, and the undercarriage transparency that thermoplastic elastomer's variant material was made is high, and toughness is high, and the quality is light, is favorable to improving unmanned aerial vehicle's safety compels to land the performance, and the warning ball that is filled with hydrogen can rise to undercarriage inside cavity top after first protective housing breaks, is convenient for warn operating personnel shock attenuation ball and has already impaired.
Furthermore, the space and the cavity between the damping rubber sleeve and the hollow spherical shell are both vacuumized, and the vacuum environment is favorable for protecting the internal structure of the damping rubber sleeve.
Further, the fuselage of unmanned aerial vehicle body adopts high-quality carbon fiber material to make, and unmanned aerial vehicle body surface scribbles anticorrosive coating, anticorrosive coating is made by ZS-711 inorganic anticorrosive coating and 200 meshes quartz powder, and anticorrosive effect is good, has physics, chemical dual protection effect, and is pollution-free to the environment, long service life.
Further, the power unit includes battery module and power module, battery module includes the battery, power module includes the engine, and power module charges for the battery when giving the drive unit power supply, and when the battery was full of the electricity, the charge switch disconnection of battery no longer charges, and when emergency such as engine breaks down, the power switch of battery was closed, replaces the engine and provides electric power for the drive unit, realizes that unmanned aerial vehicle safety compels to land.
3. Advantageous effects
Compared with the prior art, the invention has the advantages that:
(1) this scheme can realize that unmanned aerial vehicle safety compels to land, and when unmanned aerial vehicle compels to land to fall to the ground, utilizes the shock attenuation ball of undercarriage lower extreme to reduce vibrations, protects unmanned aerial vehicle, even the shock attenuation ball splits because of friction collision, remedies the ball and will remedy the department that splits in time to effectively prevent the department that splits to continue to enlarge, guarantee that the shock attenuation effect can not suddenly reduce by a wide margin, improved its protective properties greatly.
(2) The damping ball includes hollow spherical shell and damping rubber cover, and the damping rubber cover wraps up in hollow spherical shell outer end, and the damping rubber cover splices with the undercarriage lower extreme, is connected with a plurality of connecting rods between undercarriage lower extreme and the hollow spherical shell, and hollow spherical shell and damping rubber cover cooperate, are also favorable to alleviateing the quality of damping ball when guaranteeing the shock attenuation effect, alleviate unmanned aerial vehicle's flight burden.
(3) The pre-buried ball includes that first protective housing, warning ball and remedy ball, and warning ball and remedy ball all fill in first protective housing inboardly, and first protective housing is the oxide film, and pre-buried ball can utilize its inside warning ball and the effect of remedy ball to play warning and remedy after the rubber shock attenuation cover is damaged to split.
(4) The distance between the connecting rods is larger than the diameter of the rescue ball and is 1.5mm-2mm, so that the rescue ball can conveniently pass through the connecting rods and enter between the rubber damping sleeve and the hollow spherical shell to remedy the cracked part.
(5) The first protective shell is wrapped at the outer end of the first protective shell, the second protective shell is filled with remediation liquid, the first protective shell can enable the first protective shell to be between the first ball and the second ball, the first ball and the second ball are not prone to being adhered to form a lump, the first ball is convenient to roll off smoothly, and the second protective shell is used for protecting the remediation liquid.
(6) The second protective housing is the oxide film equally, and the thickness of second protective housing is 1.2-1.5 times of first protective housing thickness, and the third protective housing is 3D printing material and adopts 3D printing technique to make, mixes elasticity epoxy in the remedy liquid, and 3D printing material is degradable, also makes things convenient for the preparation of third protective housing in the environmental protection, and elasticity epoxy viscosity is high, has improved the follow-up nature of remedy liquid to the crack.
(7) The undercarriage is thermoplastic elastomer's variant material, and the warning ball is hollow transparent spherical shell, and warning ball inner surface scribbles fluorescent coating, and warns the ball intussuseption and fill and have hydrogen, and the undercarriage transparency that thermoplastic elastomer's variant material was made is high, and toughness is high, and the quality is light, is favorable to improving unmanned aerial vehicle's safe forced landing performance, and the warning ball that is filled with hydrogen can rise to undercarriage inside cavity top after first protection shell breaks, is convenient for warn operating personnel shock attenuation ball and has been impaired.
(8) The space and the cavity between the damping rubber sleeve and the hollow spherical shell are both vacuumized, and the vacuum environment is favorable for protecting the internal structure of the damping rubber sleeve.
(9) The fuselage of unmanned aerial vehicle body adopts high-quality carbon fiber material to make, and unmanned aerial vehicle body surface scribbles anticorrosive coating, and anticorrosive coating is made by ZS-711 inorganic anticorrosive coating and 200 meshes quartz powder, and anticorrosive effectual has physics, chemical dual protection effect, and is pollution-free to the environment, long service life.
(10) The power pack includes battery module and power module, battery module includes the battery, power module includes the engine, power module charges for the battery when giving the drive unit power supply, when the battery is full of the electricity, the charge switch disconnection of battery, no longer charges, when emergency such as engine breaks down, the power supply switch of battery is closed, replaces the engine and provides electric power for drive unit, realizes that unmanned aerial vehicle safety compels to land.
Drawings
FIG. 1 is an overall perspective view of the present invention;
FIG. 2 is a schematic view of the structure at the landing gear of the present invention;
FIG. 3 is a schematic view of the structure at A in FIG. 2;
FIG. 4 is a schematic structural diagram of an embedded ball according to the present invention;
FIG. 5 is a schematic structural view of a rescue ball according to the present invention;
FIG. 6 is a schematic view of a remediation ball of the present invention with the second protective shell removed;
FIG. 7 is a schematic view of the first protective shell of the present invention just after it is broken;
FIG. 8 is a schematic structural view of the warning ball of the present invention when it floats completely;
FIG. 9 is a schematic structural view of the rubber boot according to the present invention after being repaired;
fig. 10 is a schematic circuit diagram of the present invention.
The reference numbers in the figures illustrate:
1 unmanned aerial vehicle body, 2 control mechanism, 3 undercarriage, 4 damping balls, 5 damping rubber cover, 6 hollow spherical shell, 7 pre-buried balls, 8 cavitys, 9 first protective housing, 10 warning balls, 11 benefit ball, 12 second protective housing, 13 third protective housing, 14 superficial hair, 15 string hair.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention; it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and all other embodiments obtained by those skilled in the art without any inventive work are within the scope of the present invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "top/bottom", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "sleeved/connected," "connected," and the like are to be construed broadly, e.g., "connected," which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example 1:
referring to fig. 1, 2 and 10, a safe forced landing system for an unmanned aerial vehicle and an auxiliary device thereof, comprises an unmanned aerial vehicle body 1 connected with a control mechanism 2, wherein the control mechanism 2 comprises a power unit, a driving unit, a control unit and a monitoring unit, the power unit, the driving unit and the monitoring unit are all in one-way electrical connection with the control unit, the power unit is in two-way electrical connection with the driving unit, the power unit is in one-way electrical connection with the monitoring unit, the lower end of the unmanned aerial vehicle body 1 is connected with an undercarriage 3, the lower end of the undercarriage 3 is connected with a damping ball 4, a cavity 8 is formed in the undercarriage 3, a chiseling ball 7 is arranged in the cavity 8, the safe forced landing of the unmanned aerial vehicle can be realized, and when the unmanned aerial vehicle is forced landing, the damping ball 4 at the lower end of the undercarriage 3 is utilized to reduce vibration, the unmanned aerial vehicle is protected, even if the damping ball 4 cracks due to friction collision, the chiseling ball 11 can timely repair the crack, effectively prevents the crack from expanding continuously, ensures that the damping effect cannot be reduced suddenly and greatly, and greatly improves the protection performance.
Please refer to fig. 2, damping ball 4 includes hollow spherical shell 6 and yielding rubber cover 5, yielding rubber cover 5 wraps up in 6 outer ends of hollow spherical shell, and yielding rubber cover 5 splices with 3 lower extremes of undercarriage, be equipped with between yielding rubber cover 5 and the hollow spherical shell 6 and hang hair 15, it connects on 5 inner walls of yielding rubber cover to hang hair 15, be connected with a plurality of connecting rods between 3 lower extremes of undercarriage and the hollow spherical shell 6, hollow spherical shell 6 and yielding rubber cover 5 cooperate, also be favorable to alleviateing the quality of damping ball 4 when guaranteeing the shock attenuation effect, alleviate unmanned aerial vehicle's flight burden.
Referring to fig. 4, the embedded ball 7 includes a first protective shell 9, a warning ball 10 and a remedial ball 11, the warning ball 10 and the remedial ball 11 are both filled inside the first protective shell 9, the first protective shell 9 is an oxide film, and the embedded ball 7 can perform warning and remedial actions by using the warning ball 10 and the remedial ball 11 inside the embedded ball 7 after the rubber shock-absorbing sleeve 5 is damaged and cracked.
The distance between the connecting rods is larger than the diameter of the rescue ball 11 and is 1.5mm-2mm, so that the rescue ball 11 can smoothly pass through the connecting rods and enter between the rubber damping sleeve 5 and the hollow spherical shell 6 to remedy the cracked part.
Referring to fig. 5, the remedial ball 11 includes a second protective shell 12 and a third protective shell 13, the second protective shell 12 wraps the outer end of the third protective shell 13, the outer end of the third protective shell 13 is connected with floating bristles 14 capable of adhering to the hanging bristles 15, the third protective shell 13 is filled with remedial liquid, after the second protective shell 12 is broken, the third protective shell 13 filled with remedial liquid adheres to the hanging bristles 15 through the floating bristles 14, when the third protective shell 13 is squeezed, the remedial liquid can uniformly flow to repair the cracked positions, the second protective shell 12 enables the remedial ball 11 and the warning ball 10 to be difficult to adhere to and agglomerate, and meanwhile, the remedial ball 11 can roll off smoothly, and the third protective shell 13 is used for protecting the remedial liquid.
The second protective shell 12 is also an oxide film, the thickness of the second protective shell 12 is 1.2-1.5 times of the thickness of the first protective shell 9, the first protective shell 9 can be guaranteed to be firstly oxidized and broken, the second protective shell 12 is broken when the remediation ball 11 rolls down between the gap between the shock-absorbing rubber sleeve 5 and the hollow ball shell 6, the shock-absorbing rubber sleeve 5 is easy to wear and is generally at the bottom end, the appropriate concentration and flowing force of remediation liquid can guarantee that the remediation liquid can flow to the inner bottom end of the shock-absorbing rubber sleeve 5 for repairing, for the damaged parts of the upper parts of some shock-absorbing rubber sleeves 5, the third protective shell 13 filled with the remediation liquid is adhered by the hanging bristles 15 at the damaged parts, the remediation liquid flows out for repairing after the third protective shell 13 is crushed and broken, the third protective shell 13 is made of 3D printing material and is made by adopting 3D printing technology, the remediation liquid is doped with elastic epoxy resin, the 3D printing material is degradable, also makes things convenient for the preparation of third protective housing 13 in the environmental protection, and elasticity epoxy viscosity is high, has improved the follow-up nature of remedy liquid to the crack.
The space between the damping rubber sleeve 5 and the hollow spherical shell 6 and the cavity 8 are both vacuumized, and the vacuum environment is favorable for protecting the internal structure of the damping rubber sleeve.
The fuselage of unmanned aerial vehicle body 1 adopts high-quality carbon fiber material to make, and 1 surface of unmanned aerial vehicle body scribbles anticorrosive coating, and anticorrosive coating is made by ZS-711 inorganic anticorrosive coating and 200 meshes quartz powder, and is anticorrosive effectual, has physics, chemical dual protection effect, and is pollution-free to the environment, long service life.
The power pack includes battery module and power module, battery module includes the battery, power module includes the engine, power module charges for the battery when giving the drive unit power supply, when the battery is full of the electricity, the charge switch disconnection of battery, no longer charges, when emergency such as engine breaks down, the power supply switch of battery is closed, replaces the engine and provides electric power for drive unit, realizes that unmanned aerial vehicle safety compels to land.
During operation, the control mechanism 2 of the unmanned aerial vehicle comprises a power unit, a driving unit, a control unit and a monitoring unit, the power unit ensures the stable flight and the landing of the unmanned aerial vehicle, the power unit comprises a storage battery module and a power generation module, the storage battery module comprises a storage battery, the power generation module comprises an engine, the power generation module supplies power to the driving unit and charges the storage battery at the same time, when the storage battery is fully charged, a charging switch of the storage battery is disconnected and is not charged any more, when the engine breaks down and other emergency situations, a power supply switch of the storage battery is closed to supply power to the driving unit instead of the engine, the unmanned aerial vehicle is safely forced to land, once the damping rubber sleeve 5 on the damping ball 4 is damaged and cracked in friction collision, air enters a gap between the damping rubber sleeve 5 and the hollow ball shell 6 from the cracked part and then enters the cavity 8, oxygen in the first protective shell 9 contacting the air is oxidized and cracked, its inside remedy ball 11 whereabouts under the action of gravity, inside warning ball 10 that is filled with hydrogen rises along cavity 8, it has been impaired to be convenient for warn operating personnel shock attenuation ball 4, when remedy ball 11 rolls between the space between yielding rubber cover 5 and hollow spherical shell 6, second protective housing 12 breaks gradually, the third protective housing 13 that the inside packing has remedy liquid is on hanging hair 15 through floating hair 14 adhesion, when receiving the extrusion, third protective housing 13 breaks, it can the even trickling repair position of splitting to remedy liquid, effectively prevent the position of splitting to continue to enlarge, guarantee that the shock attenuation effect can not suddenly reduce by a wide margin, its protective properties has been improved greatly.
The foregoing is only a preferred embodiment of the present invention; the scope of the invention is not limited thereto. Any person skilled in the art should be able to cover the technical scope of the present invention by equivalent or modified solutions and modifications within the technical scope of the present invention.
Claims (9)
1. The utility model provides a safe forced landing system and auxiliary device for unmanned aerial vehicle, is including being connected with unmanned aerial vehicle body (1) of control mechanism (2), its characterized in that: the control mechanism (2) comprises a power unit, a driving unit, a control unit and a monitoring unit, wherein the power unit, the driving unit and the monitoring unit are all in one-way connection with the control unit, the power unit is in two-way connection with the driving unit, the power unit is in one-way connection with the monitoring unit, the lower end of the unmanned aerial vehicle body (1) is connected with an undercarriage (3), the lower end of the undercarriage (3) is connected with a damping ball (4), a cavity (8) is formed in the undercarriage (3), and a pre-buried ball (7) is arranged in the cavity (8); the embedded ball (7) comprises a first protective shell (9), a warning ball (10) and a remedial ball (11), wherein the warning ball (10) and the remedial ball (11) are both filled in the inner side of the first protective shell (9), and the first protective shell (9) is an oxidation film.
2. A forced landing system for unmanned aerial vehicles and auxiliary device thereof according to claim 1, wherein: damping ball (4) include hollow spherical shell (6) and damping rubber cover (5), damping rubber cover (5) wrap up in hollow spherical shell (6) outer end, and damping rubber cover (5) splice with undercarriage (3) lower extreme, be connected with a plurality of connecting rods between undercarriage (3) lower extreme and hollow spherical shell (6).
3. A forced landing system for unmanned aerial vehicles and auxiliary device thereof according to claim 2, wherein: the distance between the connecting rods is larger than the diameter of the rescue ball (11) and is 1.5mm-2 mm.
4. A forced landing system for unmanned aerial vehicles and auxiliary device thereof according to claim 3, wherein: the rescue ball (11) comprises a second protective shell (12) and a third protective shell (13), the second protective shell (12) wraps the outer end of the third protective shell (13), and remediation liquid is filled in the third protective shell (13).
5. A safe forced landing system for unmanned aerial vehicle and auxiliary device thereof according to claim 4, wherein: the second protective shell (12) is also an oxide film, the thickness of the second protective shell (12) is 1.2-1.5 times that of the first protective shell (9), the third protective shell (13) is made of 3D printing materials and is made by adopting a 3D printing technology, and elastic epoxy resin is doped in the remediation liquid.
6. A forced landing system for unmanned aerial vehicles and auxiliary device thereof according to claim 1, wherein: the landing gear (3) is made of a variant material of a thermoplastic elastomer, the warning ball (10) is a hollow transparent ball shell, the inner surface of the warning ball (10) is coated with a fluorescent coating, and hydrogen is filled in the warning ball (10).
7. A forced landing system for unmanned aerial vehicles and auxiliary device thereof according to claim 2, wherein: and the space between the damping rubber sleeve (5) and the hollow spherical shell (6) and the cavity (8) are both vacuumized.
8. A forced landing system for unmanned aerial vehicles and auxiliary device thereof according to claim 1, wherein: the unmanned aerial vehicle body (1) is characterized in that the unmanned aerial vehicle body is made of high-quality carbon fiber materials, an anticorrosive coating is coated on the outer surface of the unmanned aerial vehicle body (1), and the anticorrosive coating is made of ZS-711 inorganic anticorrosive paint and 200-mesh quartz powder.
9. A forced landing system for unmanned aerial vehicles and auxiliary device thereof according to claim 1, wherein: the power unit includes a battery module and a power generation module, the battery module includes a battery, and the power generation module includes an engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811002660.8A CN109131848B (en) | 2018-08-30 | 2018-08-30 | Safe forced landing system for unmanned aerial vehicle and auxiliary device thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811002660.8A CN109131848B (en) | 2018-08-30 | 2018-08-30 | Safe forced landing system for unmanned aerial vehicle and auxiliary device thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109131848A CN109131848A (en) | 2019-01-04 |
| CN109131848B true CN109131848B (en) | 2022-05-17 |
Family
ID=64829507
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811002660.8A Active CN109131848B (en) | 2018-08-30 | 2018-08-30 | Safe forced landing system for unmanned aerial vehicle and auxiliary device thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109131848B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112389644A (en) * | 2020-10-25 | 2021-02-23 | 高新轩 | Six rotor survey and drawing unmanned aerial vehicle with force is shut down |
| CN112793766A (en) * | 2021-02-04 | 2021-05-14 | 郑州航空工业管理学院 | Unmanned aerial vehicle is patrolled and examined to undercarriage folded cascade |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1669132A (en) * | 2002-07-15 | 2005-09-14 | 摩托罗拉公司 | Self-healing polymer compositions |
| CN204279927U (en) * | 2014-10-23 | 2015-04-22 | 深圳九星智能航空科技有限公司 | There is with elastic ball the rotor craft alighting gear of rotor protected effect |
| CN105820713A (en) * | 2016-05-03 | 2016-08-03 | 沈阳建筑大学 | Self-repairing coating for marine ships and preparation method thereof |
| US9517838B1 (en) * | 2014-10-03 | 2016-12-13 | John V. Howard | Remotely controlled co-axial rotorcraft for heavy-lift aerial-crane operations |
| CN107380410A (en) * | 2017-10-02 | 2017-11-24 | 张家霞 | A kind of landing damping device of unmanned plane |
| CN107539464A (en) * | 2017-07-20 | 2018-01-05 | 袁锦红 | A kind of agricultural fog machine |
| CN107600418A (en) * | 2017-10-13 | 2018-01-19 | 南京涵曦月自动化科技有限公司 | A kind of unmanned aerial vehicle (UAV) control anticollision device, collision-prevention device |
| CN108248837A (en) * | 2018-02-27 | 2018-07-06 | 广东翔龙航空技术有限公司 | A kind of unmanned plane rack stabilization control device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN206511111U (en) * | 2017-01-09 | 2017-09-22 | 广东超距未来科技有限公司 | A kind of undercarriage of unmanned plane |
-
2018
- 2018-08-30 CN CN201811002660.8A patent/CN109131848B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1669132A (en) * | 2002-07-15 | 2005-09-14 | 摩托罗拉公司 | Self-healing polymer compositions |
| US9517838B1 (en) * | 2014-10-03 | 2016-12-13 | John V. Howard | Remotely controlled co-axial rotorcraft for heavy-lift aerial-crane operations |
| CN204279927U (en) * | 2014-10-23 | 2015-04-22 | 深圳九星智能航空科技有限公司 | There is with elastic ball the rotor craft alighting gear of rotor protected effect |
| CN105820713A (en) * | 2016-05-03 | 2016-08-03 | 沈阳建筑大学 | Self-repairing coating for marine ships and preparation method thereof |
| CN107539464A (en) * | 2017-07-20 | 2018-01-05 | 袁锦红 | A kind of agricultural fog machine |
| CN107380410A (en) * | 2017-10-02 | 2017-11-24 | 张家霞 | A kind of landing damping device of unmanned plane |
| CN107600418A (en) * | 2017-10-13 | 2018-01-19 | 南京涵曦月自动化科技有限公司 | A kind of unmanned aerial vehicle (UAV) control anticollision device, collision-prevention device |
| CN108248837A (en) * | 2018-02-27 | 2018-07-06 | 广东翔龙航空技术有限公司 | A kind of unmanned plane rack stabilization control device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109131848A (en) | 2019-01-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109131848B (en) | Safe forced landing system for unmanned aerial vehicle and auxiliary device thereof | |
| CN204055195U (en) | A kind of six rotor diving aircraft | |
| CN204726664U (en) | Unmanned vehicle | |
| CN107140229B (en) | Energy supply system for staying unmanned aerial vehicle | |
| CN201390114Y (en) | Triphibian hybrid vehicle | |
| CN106828900A (en) | A kind of unmanned plane with Fu Sheng mechanisms | |
| CN102126554A (en) | Unmanned air vehicle with multiple rotary wings in plane-symmetry layout | |
| CN201494622U (en) | Wired electric flying and floating aircraft | |
| CN215753045U (en) | Hybrid vertical take-off and landing fixed wing unmanned aerial vehicle power system | |
| CN102923314A (en) | Hybrid power distribution mooring flying platform with double power sources | |
| CN109760819A (en) | A kind of structure battery component of aircraft and aircraft | |
| CN206516728U (en) | Quick-inflating type long circulating electrokinetic cell system | |
| CN208715474U (en) | A kind of multi-rotor unmanned aerial vehicle | |
| CN108945465B (en) | Battery throwing and recycling positioning device for electric multi-rotor aircraft | |
| CN217227475U (en) | Collision buffering structure of automobile energy storage battery | |
| CN206606352U (en) | A kind of strong unmanned plane of endurance | |
| CN212172552U (en) | Centrifugal clutch type hybrid power propulsion device of vertical take-off and landing fixed wing unmanned aerial vehicle | |
| CN108583929A (en) | A kind of low cost is portable to be tethered at unmanned plane | |
| CN104648671A (en) | Manned flying saucer | |
| CN204368430U (en) | Solar energy electric personal aircraft | |
| CN108790646A (en) | A kind of multi-functional flight fish in land, water and air | |
| CN206610859U (en) | Green long circulating electrokinetic cell system | |
| Lechniak et al. | Nano-electro fuel energy economy and powered aircraft operations | |
| CN206826932U (en) | A kind of unmanned plane with electricity generation system | |
| CN201357763Y (en) | Capacitor or power battery-traction electric car electric control system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20220428 Address after: 621000 No. 35 Mian'an Road, Fucheng District, Mianyang City, Sichuan Province (Science and Technology City Software Industrial Park) (cluster registration) Applicant after: SICHUAN JIUQIANG COMMUNICATION TECHNOLOGY CO.,LTD. Address before: 241080 2nd floor, s-06, Xihu Xincheng, Sanshan District, Wuhu City, Anhui Province Applicant before: WUHU YIXUN FLIGHT INTELLIGENT EQUIPMENT CO.,LTD. |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant |